LF2/Ammonia
Propellant
Original archive entry. The text, images and links below are kept as they were written.
LF2/Ammonia propellant. In Russia this combination nearly made it into production in Glushko's RD-301 engines for use in a high-performance upper stage for the Proton booster in the 1970's. However although test engines were built, fluorine was just too toxic and reactive to be safely used as a propellant. Ammonia (NH3) is a colorless liquid with a strong irritating characteristic odor.
Optimum Oxidizer to Fuel Ratio: 3.15. Temperature of Combustion: 4,510 deg K. Ratio of Specific Heats: 1.33. Density: 1.17 g/cc. Characteristic velocity c: 2,185 m/s (7,168 ft/sec). Isp Shifting: 359 sec. Isp Frozen: 330 sec. Mol: 19.30 M (63.30 ft). Oxidizer Density: 1.510 g/cc. Oxidizer Freezing Point: -219 deg C. Oxidizer Boiling Point: -188 deg C. Fuel Density: 0.604 g/cc. Fuel Freezing Point: -78 deg C. Fuel Boiling Point: -33 deg C.
Subtopics
- Proton K-4H Proposed LF2/Ammonia propellant Proton K fourth stage. Not put into production due to volatility of oxidizer.
RD-301 Glushko exotic LF2/Ammonia rocket engine. Proton K stage 4. Developed 1965-77. Developed by Glushko beginning in 1965. Planned for use in Proton K-4H high energy upper stage. Motor tested in 1977 but never flown.- RD-302 Glushko exotic LF2/Ammonia rocket engine. Developed 1960-69. Successor to RD-303 and predecessor to RD-301. Staged combustion cycle.
- RD-303 Glushko exotic LF2/Ammonia rocket engine. Developed 1960-65. Predecessor to RD-302 and RD-301.
Related
- Stages
- Proton K-4H